EP2391906B1 - Appareil et procédé pour aider les véhicules à décollage à la verticale - Google Patents

Appareil et procédé pour aider les véhicules à décollage à la verticale Download PDF

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Publication number
EP2391906B1
EP2391906B1 EP10735428.4A EP10735428A EP2391906B1 EP 2391906 B1 EP2391906 B1 EP 2391906B1 EP 10735428 A EP10735428 A EP 10735428A EP 2391906 B1 EP2391906 B1 EP 2391906B1
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EP
European Patent Office
Prior art keywords
imaging system
interest
area
transmitter
receiver
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Not-in-force
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EP10735428.4A
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German (de)
English (en)
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EP2391906A2 (fr
EP2391906A4 (fr
Inventor
Ian Dennis Longstaff
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Teledyne Australia Pty Ltd
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Teledyne Australia Pty Ltd
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Priority claimed from AU2009900337A external-priority patent/AU2009900337A0/en
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Publication of EP2391906A2 publication Critical patent/EP2391906A2/fr
Publication of EP2391906A4 publication Critical patent/EP2391906A4/fr
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    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
    • G01S13/00—Systems using the reflection or reradiation of radio waves, e.g. radar systems; Analogous systems using reflection or reradiation of waves whose nature or wavelength is irrelevant or unspecified
    • G01S13/88—Radar or analogous systems specially adapted for specific applications
    • G01S13/91—Radar or analogous systems specially adapted for specific applications for traffic control
    • G01S13/913—Radar or analogous systems specially adapted for specific applications for traffic control for landing purposes
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
    • G01S13/00—Systems using the reflection or reradiation of radio waves, e.g. radar systems; Analogous systems using reflection or reradiation of waves whose nature or wavelength is irrelevant or unspecified
    • G01S13/02—Systems using reflection of radio waves, e.g. primary radar systems; Analogous systems
    • G01S13/06—Systems determining position data of a target
    • G01S13/08—Systems for measuring distance only
    • G01S13/32—Systems for measuring distance only using transmission of continuous waves, whether amplitude-, frequency-, or phase-modulated, or unmodulated
    • G01S13/34—Systems for measuring distance only using transmission of continuous waves, whether amplitude-, frequency-, or phase-modulated, or unmodulated using transmission of continuous, frequency-modulated waves while heterodyning the received signal, or a signal derived therefrom, with a locally-generated signal related to the contemporaneously transmitted signal
    • G01S13/347—Systems for measuring distance only using transmission of continuous waves, whether amplitude-, frequency-, or phase-modulated, or unmodulated using transmission of continuous, frequency-modulated waves while heterodyning the received signal, or a signal derived therefrom, with a locally-generated signal related to the contemporaneously transmitted signal using more than one modulation frequency
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
    • G01S13/00—Systems using the reflection or reradiation of radio waves, e.g. radar systems; Analogous systems using reflection or reradiation of waves whose nature or wavelength is irrelevant or unspecified
    • G01S13/88—Radar or analogous systems specially adapted for specific applications
    • G01S13/882—Radar or analogous systems specially adapted for specific applications for altimeters
    • G—PHYSICS
    • G05—CONTROLLING; REGULATING
    • G05D—SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES
    • G05D1/00—Control of position, course, altitude or attitude of land, water, air or space vehicles, e.g. using automatic pilots
    • G05D1/04—Control of altitude or depth
    • G05D1/06—Rate of change of altitude or depth
    • G05D1/0607—Rate of change of altitude or depth specially adapted for aircraft
    • G05D1/0653—Rate of change of altitude or depth specially adapted for aircraft during a phase of take-off or landing
    • G05D1/0676—Rate of change of altitude or depth specially adapted for aircraft during a phase of take-off or landing specially adapted for landing
    • G—PHYSICS
    • G05—CONTROLLING; REGULATING
    • G05D—SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES
    • G05D1/00—Control of position, course, altitude or attitude of land, water, air or space vehicles, e.g. using automatic pilots
    • G05D1/08—Control of attitude, i.e. control of roll, pitch, or yaw
    • G05D1/0808—Control of attitude, i.e. control of roll, pitch, or yaw specially adapted for aircraft
    • G05D1/0858—Control of attitude, i.e. control of roll, pitch, or yaw specially adapted for aircraft specially adapted for vertical take-off of aircraft
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
    • G01S13/00—Systems using the reflection or reradiation of radio waves, e.g. radar systems; Analogous systems using reflection or reradiation of waves whose nature or wavelength is irrelevant or unspecified
    • G01S13/02—Systems using reflection of radio waves, e.g. primary radar systems; Analogous systems
    • G01S2013/0236—Special technical features
    • G01S2013/0245—Radar with phased array antenna
    • G01S2013/0254—Active array antenna

Definitions

  • the present application relates to apparatus and methods for assisting operators of vertical takeoff vehicles in landing operations within environments of low visual acuity.
  • the present application relates to a radar altimeter for assisting in landing operations of vertical takeoff vehicles.
  • the increased turbulence created by the rotors can create eddy currents within the particulate cloud.
  • the swirling mass of particles can lead the pilot to experience the vection illusion, a form of spatial disorientation where the helicopter appears to be turning when it is actually in a level hover.
  • a pilot not using the flight instruments for reference may instinctively try to level the aircraft, resulting in an accident.
  • the basic radar altimeter utilises a radar ranging system which measures the time delay of the signal reflected from the nearest object within a single wide beam illuminating the ground. This wide-beam is intended to monitor aircraft height even when in a bank or flying near steep slopes.
  • US patent No. 5,047,779 to Hager which is capable of tracking at least two targets.
  • the altimeter of Hager information relating to the first target is captured via a first set of radar antennas and stored before the altimeter switches to a track and store information of the second target via a second set of radar antennas.
  • US patent No. 6,750,807 also to Hager et al describes a similar scheme, but with a forward-looking scanning beam for obstacle warning. Both arrangements proposed in Hager patents simply provide range information to both targets and as such are generally useful in assisting a pilot with obstacle avoidance in flight.
  • Neither of the altimeter Hager patents is capable of providing the pilot of any useful information regarding the tomography of the desired landing surface.
  • US 2008/074312A1 discloses an imaging system for assisting operators of vertical take off vehicles in landing operations with environments of low visual acuity by profiling an area of interest, the area of interest being a desired landing surface, said system comprising
  • WO 2008/134815 discloses a collision avoidance system for use with an unmanned vehicle, the system includes a plurality of radar elements arranged parallel to the longitudinal axis of the unmanned vehicle wherein said radar elements transmit a plurality of pulses about said vehicle and receive a plurality of return signals from one or more objects within range of said vehicle. Upon detecting that one or more objects are within range of said vehicle the system determines if the object is on a course which requires evasive action and suitably alters the vehicle's course in order to avoid a collision.
  • an imaging system for assisting operators of vertical takeoff vehicles in landing operations within environments of low visual acuity by profiling an area of interest, the area of interest being a desired landing surface, said system comprising:
  • the plurality of coded signals transmitted by the transmitters may each have a different signature code allowing the receiving elements to separate out return signals for each transmitting element reflected from the area of interest.
  • the coded signals may be transmitted in accordance with a suitable multiplexing scheme such as time division multiplexing (TDM), frequency division multiplexing (FDM), code division multiplexing (CDM), or combinations of these.
  • each coded signal may each have a different signature code.
  • Each signature code may be formed by a linear frequency sweep at staggered intervals. Alternately each signature code may be formed as a differing code sequence of pulses at the same frequency.
  • each signature code may coded by applying phase or amplitude modulations.
  • each signature code may have a unique carrier frequency selected from a set of predetermined frequencies.
  • the carrier frequencies of the coded signals maybe cycled incrementally after each transmission, such that each transmitter element transmits a full set of pulses covering all the predetermined frequencies.
  • the transmission of the coded signals may be staggered, whereby each transmitter element transmits a different carrier frequency within the sequence of coded signals to that off the adjacent transmitter element/s.
  • the pulses are transmitted in the microwave or millimetre portions of the electromagnetic spectrum.
  • the transmitter and receiver elements have patterns covering +/- 60 degrees in along track and cross track.
  • the transmitter and receiver element patterns may be tilted forward to cover from +90 degrees forward-horizontal to 30 degrees behind nadir.
  • the transmitter and receiver elements have the same polarisation.
  • the transmitter and receiver elements may be formed into transmitter and receiver sub-arrays arranged orthogonal to one another. Suitably the spacing between the elements is about half a wavelength.
  • Each element within the sub-arrays may be connected in series to reduce the number of active devices.
  • the transmitter and receiver sub-arrays are arranged to form planar array wherein the transmitter and receiver elements are positioned adjacent to the array perimeter.
  • the planar array may define any suitable closed planar shape such as a circle, square, rectangle, octagon or the like.
  • the terrain profile may be displayed as a contour or mesh plot.
  • the terrain profile maybe further processed to determine a substantially level area within the area of interest, which may then be identified on the displayed contour or mesh plot.
  • a warning may be displayed if no substantially level area can be identified.
  • the warning may also include an audible warning.
  • the imaging system may also compare the terrain profile with a threshold value denoting the level clearance and flatness to safely land an aircraft within the area of interest and display suitable and unsuitable areas to the aircrafts operator.
  • a constant frequency separation is employed between the carrier frequencies of each pulses (i.e. the spacing between the carrier frequencies of each pulse in the frequency domain is identical).
  • pulse compression techniques such as step-frequency range compression can be employed to further improve range resolution.
  • the chosen coding scheme should preferably have codes which produce low time sidelobes after auto-correlation (range compression) and low or zero resultant if cross-correlated against others in the set used.
  • the synthesis of the multiple beams is conducted in accordance with a coherent Multiple Input Multiple Output (MIMO) processing technique.
  • MIMO processing includes the steps of converting the distance between each transmitter element, and each receiver element to a delay time and then removing the delay time from the received signals, before weighting and summing the pulses and signals from all the transmitter and receiver element pairs.
  • MIMO Multiple Input Multiple Output
  • the MIMO technique makes use of the fact that the signal received from the far field with a bi-static transmitter receiver pair is identical to the signal which would be received by a single mono-static transmit/receive element placed at the mid point between the bi-static pair.
  • the image computation can be based on the geometry arising from a notional plurality of transient elements.
  • the technique can also be used for signals from the nearer field, but additional processing is required to account for an ellipsoidal co-phase surface with the bi-static elements at the foci. In the far field this ellipsoid tends to a spherical surface centred on a synthetic element at the rnid-point.
  • each receiver element is able to separate the return signals in order to match them to the corresponding signals transmitted from each transmitter element (i.e. a form of multi-static processing within the array itself).
  • NxM the product of the transmitter and receiver element numbers
  • this may be achieved by transmitting from each element in turn (time division multiplexing), or by simultaneously transmitting separable code sequences from each element (code division multiplexing), or by simultaneously transmitting differing frequency sequences (for instance orthogonal frequency division multiplexing).
  • the code sequences required for signal separability can also serve the need for pulse compression.
  • Fig 1 illustrates the concept of synthesising multiple beams under the MIMO technique.
  • the coding scheme is modulated onto a carrier 101 by encoders 102a, 102b,..., 102M via mixers 103a, 103b,..., 103M to produce a set of M discrete coded signal, before being transmitted toward the area of interest 105 from transmitting elements 104a, 104b,..., 104M.
  • a set of reflected encoded signals are received by each receiver element 106a, 106b,..., 106N i.e. each receiver element captures reflected signals corresponding to the transmitted from each of the transmitter elements Tx 1 , Tx 2 ,...,Tx M .
  • the received encoded signals are then decoded by applying a decode signal 107a,107b,...,107M to each of the received signals captured ([Rx 11 , Rx 12 Rx 1M ], [Rx 21 , Rx 22 ,...,Rx 2M ], ..., [Rx N1 , Rx N2 ,...,Rx NM ]) by each of the receiver 106a, 106b,...,106N via banks of mixers 108a, 108b,...,108N.
  • the proposed radar altimeter utilises a downward looking MIMO phased array to form multiple beams, covering a relatively wide sector, +/- 60 degrees or thereabouts.
  • the distance to the ground is then measured in each beam allowing the ground profile to be formed.
  • the beams may be tilted forward to cover from +90 degrees forward (horizontal) to 30 degrees behind nadir.
  • the provision of such a forward tilt gives a greater degree of coverage in the direction of approach vector to the ground.
  • This additional cover enables the altimeter to more accurately detect other vehicles in the proximity to the current approach vector of the vehicle to the desired landing zone.
  • Such functionality is exceedingly desirable in instance where multiple vehicles are to be landed within a limited space e.g. a deck of an aircraft carrier etc.
  • FIG. 2A depicts an open array 200 arrangement which is formed from two sub-arrays 201 a, 201 b, one a transmitter array and one receiver array arranged substantially orthogonal to one another such that they form an L shape.
  • An alternative open array construction 200 is shown in Fig 2B in this case the sub-arrays 201 a, 201 b have been arranged to form a T shape. Again the sub-arrays 201 a, 201 b are aligned substantially orthogonal to one another.
  • Fig 2C depicts one possible configuration of a closed array 200 which is more commonly referred to as perimeter array.
  • the array includes 32 transmitter elements and 32 receiver elements arranged into four sub-arrays.
  • Two transmitter sub-arrays 201 a, 201 a' disposed on opposing side of the array and orthogonal to the two receiver sub-arrays 201 b, 201 b'.
  • Each of the transmitter sub-arrays 201 a, 201 a' includes 16 antenna elements arranged in banks 203 of four antennas 205.
  • Each transmission bank 203 is coupled to a switching network 207. The selection of which transmission elements 205 are active during the transmission cycle is determined by the switching network 207 which opens and closes the appropriate switches to activate the appropriate antenna element 203 based on the chosen multiplexing scheme.
  • the receiver sub-arrays 202b, 202b' are arranged into banks 204 of four antenna elements 206.
  • Each receiver bank 204 is coupled to a switching network 208 which passes the signals received by the active receiver elements 206 to the backend processing section.
  • each of the antenna elements in the sub-arrays 201 a, 201 a' and 202b, 202b' have the same polarisation.
  • the antenna elements should also be selected to provide sufficient beam-width (element directional pattern) to illuminate a sufficient area direct beneath and beyond the extremities of the vehicle e.g. +/- 60 degrees in along track and cross track.
  • the spacing between the elements would need to be slightly greater than a half wavelength sufficient to synthesise 32 beams within the +/-60 degree element beam.
  • the array shown in Fig 2C is a square parameter array it will be appreciated by those skilled in the art that the array may be in the form of any suitable shape where multiple combinations of transmitter/receiver pairs allow the formation of a filled aperture.
  • Such configurations might include a rectangle, a T or L shape, a circle, octagon or the like.
  • Fig 3 depicts the use of a MIMO array in a ground profiling operation in a radar altimeter according to one embodiment of the present invention.
  • the aircraft 301 scans of the desired landing zone 302.
  • the synthesised beams each form a narrow cone.
  • the illuminated patch 302 is wide at higher altitudes.
  • the aircraft 301 descends smaller features of the ground profile can be resolved.
  • Each of the transmitter elements 203 in the array 200 radiate a sequence of M differing signals, the ground reflections from which are captured by each of the N receiver element 206 of the array. Each of the N receiver elements then separates out the M received ground reflections from the M transmitters to produce MxN differing received channels.
  • the channels are formed into MxN beams by co-phasing the data channels to remove the phase shifts associated with a particular angle of arrival and then summing. Then by suitably filtering the data in each beam a set of range profiles is formed, thereby allowing the time delay of the return signal via the nearest point in each beam be measured and converted to a distance. These distance measures are then converted into a profile showing the ground and any obstacles 303 on the ground, allowing the suitability of a selected landing zone to be assessed.
  • a signal detector with a short sampling widow is utilised.
  • the signal detector measures the range to the nearest point in each beam with leading edge trackers which search out from zero range to detect the first return.
  • the first return in each beam is then tracked with a suitable early-late gate or similar. If the signal fades the tracker stays locked for a short interval and if the signal has not returned in this interval the tracker repeatedly searches out from zero again until it can lock onto the return signal.
  • the resultant ground profile may be displayed to the pilot for assessment as a contour plot or as a mesh plot. This would allow the pilot to independently judge which regions within a surveyed area may be suitable landing sites.
  • the altimeter may employ an algorithm to automatically determine the suitability of surveyed area for landing. The algorithm may incorporate such considerations as whether there is adequate rotor/wing clearance, whether the ground slope is sufficiently parallel to the landing gear and determining the height at which any obstacles on the landing zone project above the landing surface, in order to decide which regions within a surveyed area are suitable for landing. Areas identified as suitable and unsuitable could then be displayed to the pilot via display unit to further assist the pilot in the selection of a landing zone.
  • An audible warning may also be provided if the ground in view has a profile falling outside the specification for a safe landing. If a vertical reference is available the display could be referenced to this, otherwise the terrain display would be referenced to the pitch and roll of the vehicle. In this case the image of the ground profile would tilt according to the vehicle's angle with respect to the ground.
  • a radar altimeter with a leading edge tracker can deliver the required accuracy (+/- 2 ft) with a 20 ns pulse, but waveforms which can be time-compressed to that length (pulse compression) are also suitable.

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  • Engineering & Computer Science (AREA)
  • Remote Sensing (AREA)
  • Radar, Positioning & Navigation (AREA)
  • Physics & Mathematics (AREA)
  • General Physics & Mathematics (AREA)
  • Computer Networks & Wireless Communication (AREA)
  • Electromagnetism (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Automation & Control Theory (AREA)
  • Radar Systems Or Details Thereof (AREA)

Claims (27)

  1. Système d'imagerie destiné à aider des opérateurs de véhicules à décollage vertical au cours d'opérations d'atterrissage dans des environnements à faible visibilité, en profilant une zone d'intérêt (302), la zone d'intérêt (302) étant une zone d'atterrissage souhaitée, ledit système comprenant :
    une pluralité d'éléments émetteurs (104, 205), chaque élément émetteur (104, 205) émettant un signal codé vers la zone d'intérêt (302) ;
    une pluralité d'éléments récepteurs (106, 206), chaque élément récepteur (106, 206) recevant une pluralité de signaux retour provenant de la zone d'intérêt (302) et correspondant aux signaux codés transmis ; et
    au moins un processeur raccordé aux éléments récepteurs. (106, 206) pour recevoir les signaux retour provenant de ceux-ci, ledit processeur étant adapté pour:
    séparer les signaux retour pour chaque trajet d'émetteur à récepteur reçu par chacun des éléments récepteurs (106, 206) pour former une pluralité de canaux de données ;
    former une pluralité de faisceaux à partir de la pluralité de canaux de données en co-phasant les canaux de données pour supprimer les déphasages associés à chacun des angles d'arrivée des signaux reçus, et en additionnant les canaux de données de chaque récepteur, et chaque faisceau incluant un premier signal reçu ;
    produire un ensemble de profils de plage à partir des données contenues dans chacun de la pluralité de faisceaux ;
    mesurer la distance jusqu'au point le plus proche dans chaque faisceau, sur la base d'un temps de retard pour la réception du premier signal retour reçu dans chaque faisceau ;
    produire un profil de terrain avec une valeur seuil indiquant des niveaux de dégagement et de planéité pour faire atterrir le véhicule à décollage vertical en toute sécurité dans la zone d'intérêt pour déterminer des zones appropriées et inappropriées identifiées sur le profil de terrain.
  2. Système d'imagerie selon la revendication 1, dans lequel les signaux codés sont transmis selon un système de multiplexage par répartition dans le temps, le retard entre la transmission de chaque signal codé étant suffisant pour permettre à tous les signaux retour provenant de la zone d'intérêt (302) de se dissiper avant la transmission du signal codé suivant.
  3. Système d'imagerie selon l'une quelconque des revendications 1 et 2, dans lequel les signaux codés présentent respectivement un code de signature différent.
  4. Système d'imagerie selon la revendication 3, dans lequel chaque code de signature est formé par un balayage de fréquence linéaire à des intervalles échelonnés.
  5. Système d'imagerie selon la revendication 3, dans lequel chaque code de signature est formé comme une séquence de code différente d'impulsions à la même fréquence.
  6. Système d'imagerie selon la revendication 5, dans lequel chaque code de signature est formé par une modulation de phase ou d'amplitude.
  7. Système d'imagerie selon la revendication 1, dans lequel la pluralité de signaux codés est transmise selon un système de multiplexage par répartition en fréquence (FDM).
  8. Système d'imagerie selon la revendication 1, dans lequel les signaux codés présentent des codes de signature différents, chaque code de signature présentant une fréquence porteuse unique sélectionnée parmi un ensemble de fréquences prédéterminées, pour permettre à l'au moins un processeur de séparer des signaux retour pour chaque élément émetteur réfléchi à partir de la zone d'intérêt (302).
  9. Système d'imagerie selon la revendication 8, dans lequel les fréquences porteuses des impulsions sont cadencées progressivement après chaque émission, de telle façon que chaque élément émetteur (104, 205) émette un ensemble complet d'impulsions couvrant toutes les fréquences prédéterminées.
  10. Système d'imagerie selon la revendication 1, dans lequel les impulsions sont transmises selon un système de multiplexage par répartition en fréquence orthogonal (OFDM).
  11. Système d'imagerie selon la revendication 10, dans lequel les signaux codés présentent chacun un code de signature différent présentant une fréquence porteuse unique sélectionnée parmi un ensemble de fréquences prédéterminées, pour permettre à l'au moins un processeur de séparer des signaux retour pour chaque élément émetteur (104, 205) réfléchi à partir de la zone d'intérêt (302).
  12. Système d'imagerie selon la revendication 10 ou 11, dans lequel l'émission des signaux codés est échelonnée, moyennant quoi chaque élément émetteur (104, 205) émet une fréquence porteuse différente dans la séquence de signaux codés par rapport à celle des éléments émetteurs (104, 205) adjacents.
  13. Système d'imagerie selon l'une quelconque des revendications précédentes, dans lequel les configurations d'éléments émetteurs et récepteurs couvrent +/-60 degrés sur un trajet longitudinal et un trajet transversal.
  14. Système d'imagerie selon l'une quelconque des revendications précédentes, dans lequel les configurations d'éléments émetteurs et récepteurs sont inclinées vers l'avant pour couvrir entre +90 degrés horizontalement vers l'avant et 30 degrés derrière le nadir.
  15. Système d'imagerie selon l'une quelconque des revendications précédentes, dans lequel les signaux codés rayonnés par chaque élément émetteur (104, 205) sont dans la portion microonde ou millimétrique du spectre électromagnétique.
  16. Système d'imagerie selon l'une quelconque des revendications précédentes, dans lequel le profil de terrain est affiché comme un tracé de mailles ou un tracé de contours.
  17. Système d'imagerie selon la revendication 1, dans lequel un avertisseur s'affiche si aucune zone appropriée ne peut être identifiée.
  18. Système d'imagerie selon la revendication 17, dans lequel l'avertisseur comprend en outre un signal sonore.
  19. Système d'imagerie selon l'une quelconque des revendications précédentes, dans lequel les éléments émetteurs et récepteurs (104, 205) (106, 206) sont divisés en sous-réseaux d'émetteurs et de récepteurs (201a, 201a') (201b, 201 b').
  20. Système d'imagerie selon la revendication 19, dans lequel les sous-réseaux d'émetteurs et de récepteurs (201 a, 201 a') (201 b, 201 b') sont disposés de façon orthogonale les uns par rapport aux autres.
  21. Système d'imagerie selon la revendication 19 ou la revendication 20, dans lequel chaque élément dans les sous-réseaux (201a, 201a') (201 b, 201 b') est relié en séquence pour réduire le nombre de dispositifs actifs.
  22. Système d'imagerie selon l'une quelconque des revendications 3 à 12, dans lequel une compression d'impulsion est appliquée.
  23. Système d'imagerie selon l'une quelconque des revendications précédentes, dans lequel la formation de la pluralité de faisceaux comprend en outre un déphasage de chacun des signaux retour reçus séparés, par chaque élément récepteur (106, 206).
  24. Système d'imagerie selon l'une quelconque des revendications précédentes, dans lequel le premier signal renvoyé dans chaque faisceau est pisté.
  25. Procédé destiné à assister des opérateurs de véhicules à décollage vertical au cours des opérations d'atterrissage dans des environnements à faible visibilité, en prospectant une zone d'intérêt pour produire un profil de terrain, la zone d'intérêt (302) étant une surface d'atterrissage souhaitée, ledit procédé comprenant les étapes suivantes :
    transmission d'une pluralité de signaux codés vers la zone d'intérêt (302), la pluralité de signaux codés étant transmise par une pluralité d'éléments émetteurs (104, 205), chaque élément émetteur (104, 205) émettant un signal codé ;
    réception, au niveau d'une pluralité d'éléments récepteurs (106, 206), d'une pluralité de signaux retour provenant de la zone d'intérêt (302) correspondant aux signaux codés transmis ; et
    apport de la pluralité de signaux retour à un processeur, le processeur exécutant les étapes suivantes :
    séparation des signaux retour pour chaque trajet d'émetteur à récepteur reçu par chacun des éléments récepteurs pour former une pluralité de canaux de données ;
    formation d'une pluralité de faisceaux à partir de la pluralité de canaux de données en co-phasant les canaux de données pour supprimer les déphasages associés à chacun des angles d'arrivée des signaux reçus, et en additionnant les canaux de données de chaque récepteur, et chaque faisceau incluant un premier signal reçu ;
    production d'un ensemble de profils de plage à partir des données contenues dans chacun de la pluralité de faisceaux ;
    mesure de la distance jusqu'au point le plus proche dans chaque faisceau, sur la base d'un temps de retard pour la réception du premier signal retour reçu dans chaque faisceau ;
    production d'un profil de terrain de la zone d'intérêt (302) à partir des mesures de distance ;
    comparaison du profil de terrain avec une valeur seuil indiquant des niveaux de dégagement et de planéité pour faire atterrir le véhicule à décollage vertical en toute sécurité dans la zone d'intérêt (302) afin de déterminer des zones appropriées et inappropriées ; et
    affichage d'une image du profil de terrain de la zone d'intérêt (302) avec les zones appropriées et inappropriées identifiées sur le profil de terrain.
  26. Procédé selon la revendication 25, dans lequel les signaux codés rayonnés par chaque élément émetteur (104, 205) sont dans la portion microonde ou millimétrique du spectre électromagnétique.
  27. Procédé selon la revendication 25 ou 26, dans lequel l'étape d'affichage du profil de terrain comprends l'affichage du profil de terrain comme un tracé de mailles ou un tracé de contours.
EP10735428.4A 2009-01-30 2010-01-28 Appareil et procédé pour aider les véhicules à décollage à la verticale Not-in-force EP2391906B1 (fr)

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AU2009900337A AU2009900337A0 (en) 2009-01-30 Apparatus and method for assisting vertical takeoff vehicles
PCT/AU2010/000082 WO2010085846A2 (fr) 2009-01-30 2010-01-28 Appareil et procédé pour aider les véhicules à décollage à la verticale

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EP2391906A2 EP2391906A2 (fr) 2011-12-07
EP2391906A4 EP2391906A4 (fr) 2013-11-06
EP2391906B1 true EP2391906B1 (fr) 2016-12-07

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US9041587B2 (en) 2015-05-26
US20110279669A1 (en) 2011-11-17
EP2391906A2 (fr) 2011-12-07
WO2010085846A2 (fr) 2010-08-05
AU2010200313A1 (en) 2010-08-19
US8427360B2 (en) 2013-04-23
EP2391906A4 (fr) 2013-11-06
AU2010200313B2 (en) 2015-10-29
WO2010085846A3 (fr) 2010-10-28
IL213904A0 (en) 2011-07-31
US20140125511A1 (en) 2014-05-08

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